US10773784B2 - Floor module of an aircraft cargo hold - Google Patents

Floor module of an aircraft cargo hold Download PDF

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US10773784B2
US10773784B2 US15/558,698 US201615558698A US10773784B2 US 10773784 B2 US10773784 B2 US 10773784B2 US 201615558698 A US201615558698 A US 201615558698A US 10773784 B2 US10773784 B2 US 10773784B2
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floor
cover element
module according
floor module
cover
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US20180111674A1 (en
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Thomas Huber
Richard Holzner
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Telair International GmbH
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Telair International GmbH
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Priority claimed from DE102015104230.4A external-priority patent/DE102015104230B4/en
Priority claimed from DE102015117571.1A external-priority patent/DE102015117571B3/en
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Assigned to TELAIR INTERNATIONAL GMBH reassignment TELAIR INTERNATIONAL GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HOLZNER, RICHARD, HUBER, THOMAS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • B64C1/20—Floors specially adapted for freight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like

Definitions

  • the invention relates to a floor module of an aircraft cargo hold.
  • Cargo which is introduced through a door into the cargo hold of an aircraft must be transported further in this cargo hold and secured in the cargo hold.
  • the floor of such a cargo hold is preferably formed in a modular manner, as is known, for example, from EP 1 646 556 B1.
  • a floor module of an aircraft cargo hold comprising a cover element and a floor element which is spaced apart from the cover element at least in some segments and which is attached to an underside of the cover element, in such a way that the cover element is designed as an integrative surface element which has mounting regions, in which freight-handling systems such as rollers, latches or PDUs can be mounted and in which the cover element is lowered to a level of the floor element.
  • An essential point of the invention is thus that, in contrast to a technical solution, as is known, for example, from EP 0 912 394 B8, the floor element does not form a simple plate. Instead, a three-dimensional part is produced, in which the cover element is only lowered in some areas where a component has to be countersunk or has to be connected to the floor element for fastening to underlying structures.
  • the present invention is suitable for use as a floor module in the area of a cargo hold door, wherein the cover element then has receiving openings for receiving ball elements.
  • the floor element is connected to circumferential edges of the cover element and seals it essentially tightly in downward direction. This ensures that the cargo hold is sealed off from the bilge, which is important for example when halon is injected in case of fire.
  • the floor element is designed in such a way that leaking liquids, in particular water entrained with the load, can be collected and discharged.
  • the cover element is preferably at least twice, but especially preferably at least three to five times, as thick as the floor element. Therefore, notice is taken here that such elements which must absorb loads perpendicular to the surface are formed much more strongly than those elements which do not have to absorb such loads. Particularly when spherical elements are mounted in the floor element, they are introduced by “suspension” into the cover element and connected to it. Separate reinforcements of the cover element in the areas in which the ball elements are installed can be provided.
  • the cover element has on at least one edge an upwardly arched section for covering the aircraft fuselage. On one edge only when the floor module is installed in the area of the aircraft door. Otherwise, these curved portions are provided on both sides of a cover element. This leads to a further simplification in the manufacture and assembly of the overall arrangement. In addition, the segment which is curved towards the flat surface of the cover element leads to a stiffening of the overall arrangement.
  • the floor module preferably has connecting elements between the cover element and the floor element.
  • a connecting element can, for example, comprise tube sleeves, by means of which fastening means, in particular screws for fastening freight-handling systems, e.g. tie-down elements, can be connected directly to transverse beams of the cargo hold.
  • fastening means in particular screws for fastening freight-handling systems, e.g. tie-down elements
  • tie-down elements e.g. tie-down elements
  • the cover element is preferably firmly connected to the handling unit common to the floor element, which considerably facilitates assembly.
  • the cover element and/or the floor element is preferably constructed as a hybrid composite part, e.g. with carbon and/or glass fibre reinforcement. This allows the desired three-dimensional shaping to take place in a heatable press mould, so that a particularly efficient production of the floor module is ensured with high strength and low weight.
  • functional rails which can be attached to the floor module and are provided with the customary freight-handling systems.
  • all elements required in the area of a cargo hold door such as stop rollers or overrideable latches, which prevent the rolling back of ULDs, are initially fastened in the functional rail, whereupon the entire functional rail is then connected to the floor module.
  • This functional rail can then in turn fasten the floor module to the mounting structures of the aircraft.
  • functional rails for the receiving latches or PDUs which are fixed in middle sections of the floor modules.
  • the cover element has peripherally-mounted stop rails, which therefore do not have to be mounted separately in the cargo hold, and in addition ensure a further stiffening of the floor modules.
  • connecting chambers are preferably provided in the floor element for connecting and/or leading out connecting cables.
  • FIG. 1 shows a prior art cargo hold with a floor module
  • FIG. 2 shows a perspective top view of an embodiment of a floor module
  • FIG. 3 shows a perspective bottom view of the module according to FIG. 2 .
  • FIG. 4 shows a planar bottom view of the module according to FIG. 2 or 3 .
  • FIG. 5 shows a top view of the floor module according to FIGS. 2-4 .
  • FIG. 6 shows a side view along line VI-VI of FIG. 5 .
  • FIG. 7 shows a sectional view along the line VII-VII of FIG. 5 .
  • FIG. 8 shows a sectional view along the line VIII-VIII of FIG. 6 .
  • FIG. 9 shows a sectional view along line IX-IX of FIG. 5 .
  • FIG. 10 shows a sectional view along the line X-X of FIG. 5 .
  • FIG. 11 shows an enlarged view corresponding to the region XI of FIG. 10 .
  • FIG. 12 shows a representation of the overall module with its individual parts
  • FIG. 13 shows a bottom view of a further floor module
  • FIG. 14 shows a top view of the floor module according to FIG. 13 .
  • FIG. 15 shows a sectional view along the line XV-XV of FIG. 14 .
  • FIG. 16 shows a perspective view of the region XVI of FIG. 15 .
  • FIG. 17 shows a sectional view along line XVII-XVII of FIG. 16 and
  • FIG. 18 shows a sectional view along line XVIII-XVIII of FIG. 16 .
  • a floor module is provided in the region of a cargo hold door 2 , said floor module comprising transverse beams 4 which are fastened to frames 3 .
  • this floor module ball elements, PDUs, bolts, rollers and similar functional elements are mounted, which are necessary in a cargo hold of an aircraft.
  • the frames 3 of the aircraft are covered by cover surfaces 23 .
  • the present invention which is explained below with reference to FIGS. 2 to 12 , is concerned with such a floor module, wherein a floor module is shown as an example in this case, which is attached (as explained above) in the region of a cargo hold door 2 .
  • a floor module has a particular plurality of individual elements, in particular ball elements, but also PDUs, bolts and the like arranged in different orientations.
  • the invention is not limited to such a floor module installed in the region of a cargo hold door.
  • a cover element 10 is provided which is covered downwards by a floor element 20 .
  • the cover element 10 is connected directly to the floor element 20 (see FIG. 11 for example) or by interposing further elements (see FIG. 9 ).
  • the floor element 20 comprises mounting regions 30 (see especially FIG. 12 ) in which a PDU 8 (see FIG. 2 ) or a functional rail 40 (see FIG. 12 ) for accommodating PDUs, bolts, rollers or similar functional elements can be mounted.
  • the mounting region 30 is formed in such a way that the cover element 10 descends downwardly and rests on the floor element 20 , or descends at least to its average level.
  • the cover element 10 rests directly on the floor element 20 where the floor module extends over a transverse beam 4 .
  • the floor element 20 furthermore has, in the middle regions, a trough structure 21 , which conducts incoming water to an outlet connection 22 , from which the water can be discharged.
  • a plurality of receiving openings 11 for ball elements are provided.
  • connection cables 27 are guided to those functional units which require such connecting cables, i.e. to PDUs or sensors (see FIG. 3 ).
  • tie-down elements 9 are provided in the cover element 10 which are fastened to transverse beams 4 by means of bolts (not shown), wherein the bolts are guided through tube sleeves 25 (see FIGS. 9 and 10 ), which in turn connect the cover element 10 to the floor element 20 .
  • These sleeves thus simultaneously constitute a stiffening member between the cover element 10 and the floor element 20 .
  • Further stiffening members in the form of a support web 24 are also provided between cover elements 10 and floor elements 20 .
  • the edges of the floor element 20 and the cover element 10 are curved upwards in such a way that the cover element 10 simultaneously forms the cover surface 23 mentioned above.
  • a stop rail 41 is also provided, which further peripherally stiffens the floor module.
  • a cover part 10 is connected to a floor part 20 , in particular on the edge side. This produces a component which traverses the entire cargo hold and which already has considerable stability due to the three-dimensional structure with the lowered mounting regions 30 .
  • Particularly stressed areas such as the entrance area in the region of the cargo hold door 2 for example can be connected, as shown here, to a functional rail 40 which is inserted between the cover element 10 and the floor element 20 in the edges thereof, as shown in FIG. 9 for example.
  • the further functional rail 40 shown in FIG. 12 which is inserted into the central regions of the floor module, is provided for accommodating the functional elements, in particular for reasons of stability enhancement and assembly simplification.
  • the floor module shown in FIGS. 13 to 18 is designed as a bulk module, thus serving to fasten the load to be lashed, for which purpose tie-down elements are provided, which are formed here as “seat rail sections” into which eyelets or hooks can be suspended. These seat rail sections are held in place during transport and assembly by O-rings 12 . After the tie-down element 9 has been fastened to a transverse beam 4 via its fastening holes 13 , the O-ring serves as a seal. In this bulk module, the cover element 10 is provided with reinforcing ribs 14 .
  • an essential point of the invention is that by the use of preferably integral components which are lighter on the one hand and are provided with a larger area and shaped in a three-dimensional manner on the other hand, reduced weight is ensured at the same time with sufficient stability and optimal assembly facilitation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Connection Of Plates (AREA)
  • Body Structure For Vehicles (AREA)

Abstract

A floor module for an aircraft cargo hold including a cover element and a floor element which is spaced apart from the cover element at least in some segments and which is attached to an underside of the cover element. The cover element includes receiving openings for receiving ball elements. The cover element and the floor element can be formed as a hybrid composite part.

Description

CROSS REFERENCE TO RELATED APPLICATIONS
This application is a U.S. nationalization under 35 U.S.C. § 371 of International Application No. PCT/EP2016/056083, filed Mar. 21, 2016, which claims priority to German Patent Application No. 10 2015 104 230.4, filed Mar. 20, 2015, and German Patent Application No. 10 2015 117 571.1, filed Oct. 15, 2015. The disclosures set forth in the referenced applications are incorporated herein by reference in their entireties.
BACKGROUND OF THE INVENTION
The invention relates to a floor module of an aircraft cargo hold.
Cargo which is introduced through a door into the cargo hold of an aircraft must be transported further in this cargo hold and secured in the cargo hold. The floor of such a cargo hold is preferably formed in a modular manner, as is known, for example, from EP 1 646 556 B1.
A major problem in the construction of such a cargo hold floor is the contradictory demand for great stability and low weight. Moreover, neither the individual components nor the installation thereof may be too complex, since this increases costs.
BRIEF SUMMARY OF THE INVENTION
It is the object of the invention to provide a floor module of an aircraft of the type mentioned in the introduction above which makes it possible to achieve a high degree of stability combined with low production costs and installation costs at low weight.
This object is achieved by a floor module as disclosed herein.
In particular, this object is achieved by a floor module of an aircraft cargo hold, comprising a cover element and a floor element which is spaced apart from the cover element at least in some segments and which is attached to an underside of the cover element, in such a way that the cover element is designed as an integrative surface element which has mounting regions, in which freight-handling systems such as rollers, latches or PDUs can be mounted and in which the cover element is lowered to a level of the floor element.
An essential point of the invention is thus that, in contrast to a technical solution, as is known, for example, from EP 0 912 394 B8, the floor element does not form a simple plate. Instead, a three-dimensional part is produced, in which the cover element is only lowered in some areas where a component has to be countersunk or has to be connected to the floor element for fastening to underlying structures.
This three-dimensional deformation with elevations and depressions already results in a higher stability of the overall arrangement, so that a thinner material can be used.
In particular, the present invention is suitable for use as a floor module in the area of a cargo hold door, wherein the cover element then has receiving openings for receiving ball elements.
Preferably, the floor element is connected to circumferential edges of the cover element and seals it essentially tightly in downward direction. This ensures that the cargo hold is sealed off from the bilge, which is important for example when halon is injected in case of fire.
Preferably, the floor element is designed in such a way that leaking liquids, in particular water entrained with the load, can be collected and discharged.
The cover element is preferably at least twice, but especially preferably at least three to five times, as thick as the floor element. Therefore, notice is taken here that such elements which must absorb loads perpendicular to the surface are formed much more strongly than those elements which do not have to absorb such loads. Particularly when spherical elements are mounted in the floor element, they are introduced by “suspension” into the cover element and connected to it. Separate reinforcements of the cover element in the areas in which the ball elements are installed can be provided.
The cover element has on at least one edge an upwardly arched section for covering the aircraft fuselage. On one edge only when the floor module is installed in the area of the aircraft door. Otherwise, these curved portions are provided on both sides of a cover element. This leads to a further simplification in the manufacture and assembly of the overall arrangement. In addition, the segment which is curved towards the flat surface of the cover element leads to a stiffening of the overall arrangement.
The floor module preferably has connecting elements between the cover element and the floor element. This results in an increased stiffness of the overall arrangement. Such a connecting element can, for example, comprise tube sleeves, by means of which fastening means, in particular screws for fastening freight-handling systems, e.g. tie-down elements, can be connected directly to transverse beams of the cargo hold. In this case, “one kills two birds with one stone”, because, on the one hand, the fastening of the fastening means which absorbs the necessary tensioning force is enabled by the sleeves and, on the other hand, the connection of the cover element and the floor element is ensured by these sleeves.
The cover element is preferably firmly connected to the handling unit common to the floor element, which considerably facilitates assembly.
The cover element and/or the floor element is preferably constructed as a hybrid composite part, e.g. with carbon and/or glass fibre reinforcement. This allows the desired three-dimensional shaping to take place in a heatable press mould, so that a particularly efficient production of the floor module is ensured with high strength and low weight.
Further increased stability with facilitated assembly at the same time is ensured by functional rails, which can be attached to the floor module and are provided with the customary freight-handling systems. For example, all elements required in the area of a cargo hold door, such as stop rollers or overrideable latches, which prevent the rolling back of ULDs, are initially fastened in the functional rail, whereupon the entire functional rail is then connected to the floor module. This functional rail can then in turn fasten the floor module to the mounting structures of the aircraft. The same applies to functional rails for the receiving latches or PDUs, which are fixed in middle sections of the floor modules.
Preferably, the cover element has peripherally-mounted stop rails, which therefore do not have to be mounted separately in the cargo hold, and in addition ensure a further stiffening of the floor modules.
In order to be able to allow the economical and neat wiring of active elements such as PDUs or sensors, connecting chambers are preferably provided in the floor element for connecting and/or leading out connecting cables.
From the above, it is also established that a method for producing a described floor module is claimed as according to the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
An embodiment of the invention is explained in closer detail below with reference to the drawings, wherein:
FIG. 1 shows a prior art cargo hold with a floor module,
FIG. 2 shows a perspective top view of an embodiment of a floor module,
FIG. 3 shows a perspective bottom view of the module according to FIG. 2,
FIG. 4 shows a planar bottom view of the module according to FIG. 2 or 3,
FIG. 5 shows a top view of the floor module according to FIGS. 2-4,
FIG. 6 shows a side view along line VI-VI of FIG. 5,
FIG. 7 shows a sectional view along the line VII-VII of FIG. 5,
FIG. 8 shows a sectional view along the line VIII-VIII of FIG. 6,
FIG. 9 shows a sectional view along line IX-IX of FIG. 5,
FIG. 10 shows a sectional view along the line X-X of FIG. 5,
FIG. 11 shows an enlarged view corresponding to the region XI of FIG. 10,
FIG. 12 shows a representation of the overall module with its individual parts,
FIG. 13 shows a bottom view of a further floor module,
FIG. 14 shows a top view of the floor module according to FIG. 13,
FIG. 15 shows a sectional view along the line XV-XV of FIG. 14,
FIG. 16 shows a perspective view of the region XVI of FIG. 15,
FIG. 17 shows a sectional view along line XVII-XVII of FIG. 16 and
FIG. 18 shows a sectional view along line XVIII-XVIII of FIG. 16.
 DETAILED DESCRIPTION OF THE INVENTION
In the following description, the same reference numerals will be used for the same and similarly acting parts.
Firstly, a cargo hold with a floor module is described on the basis of the enclosed “prior art” drawing, as is known from EP 1 646 556 B1.
In a cargo hold 1 of an aircraft, a floor module is provided in the region of a cargo hold door 2, said floor module comprising transverse beams 4 which are fastened to frames 3. On this floor module, ball elements, PDUs, bolts, rollers and similar functional elements are mounted, which are necessary in a cargo hold of an aircraft. Separately from the module, the frames 3 of the aircraft are covered by cover surfaces 23.
The present invention, which is explained below with reference to FIGS. 2 to 12, is concerned with such a floor module, wherein a floor module is shown as an example in this case, which is attached (as explained above) in the region of a cargo hold door 2. Such a floor module has a particular plurality of individual elements, in particular ball elements, but also PDUs, bolts and the like arranged in different orientations. However, the invention is not limited to such a floor module installed in the region of a cargo hold door.
According to the drawings, a cover element 10 is provided which is covered downwards by a floor element 20. In its edge regions, the cover element 10 is connected directly to the floor element 20 (see FIG. 11 for example) or by interposing further elements (see FIG. 9).
The floor element 20 comprises mounting regions 30 (see especially FIG. 12) in which a PDU 8 (see FIG. 2) or a functional rail 40 (see FIG. 12) for accommodating PDUs, bolts, rollers or similar functional elements can be mounted.
The mounting region 30 is formed in such a way that the cover element 10 descends downwardly and rests on the floor element 20, or descends at least to its average level. The cover element 10 rests directly on the floor element 20 where the floor module extends over a transverse beam 4.
The floor element 20 furthermore has, in the middle regions, a trough structure 21, which conducts incoming water to an outlet connection 22, from which the water can be discharged.
In the embodiment of the invention shown here, a plurality of receiving openings 11 for ball elements are provided.
Furthermore, the floor element 20 has downwardly projecting connection chambers 26, through which connection cables 27 are guided to those functional units which require such connecting cables, i.e. to PDUs or sensors (see FIG. 3).
Furthermore, tie-down elements 9 are provided in the cover element 10 which are fastened to transverse beams 4 by means of bolts (not shown), wherein the bolts are guided through tube sleeves 25 (see FIGS. 9 and 10), which in turn connect the cover element 10 to the floor element 20. These sleeves thus simultaneously constitute a stiffening member between the cover element 10 and the floor element 20. Further stiffening members in the form of a support web 24 (see FIGS. 9 and 10) are also provided between cover elements 10 and floor elements 20.
As shown in FIG. 11, the edges of the floor element 20 and the cover element 10 are curved upwards in such a way that the cover element 10 simultaneously forms the cover surface 23 mentioned above. In this region, a stop rail 41 is also provided, which further peripherally stiffens the floor module.
When a floor module of this kind is assembled, as shown in FIG. 12, a cover part 10 is connected to a floor part 20, in particular on the edge side. This produces a component which traverses the entire cargo hold and which already has considerable stability due to the three-dimensional structure with the lowered mounting regions 30.
Particularly stressed areas, such as the entrance area in the region of the cargo hold door 2 for example can be connected, as shown here, to a functional rail 40 which is inserted between the cover element 10 and the floor element 20 in the edges thereof, as shown in FIG. 9 for example.
The further functional rail 40 shown in FIG. 12, which is inserted into the central regions of the floor module, is provided for accommodating the functional elements, in particular for reasons of stability enhancement and assembly simplification.
The floor module shown in FIGS. 13 to 18 is designed as a bulk module, thus serving to fasten the load to be lashed, for which purpose tie-down elements are provided, which are formed here as “seat rail sections” into which eyelets or hooks can be suspended. These seat rail sections are held in place during transport and assembly by O-rings 12. After the tie-down element 9 has been fastened to a transverse beam 4 via its fastening holes 13, the O-ring serves as a seal. In this bulk module, the cover element 10 is provided with reinforcing ribs 14.
It is apparent from the above that an essential point of the invention is that by the use of preferably integral components which are lighter on the one hand and are provided with a larger area and shaped in a three-dimensional manner on the other hand, reduced weight is ensured at the same time with sufficient stability and optimal assembly facilitation.
LIST OF REFERENCE NUMERALS
  • 1 Cargo hold
  • 2 Cargo hold door
  • 3 Frames
  • 4 Transverse beams
  • 5 Deflecting roller
  • 6 Roller
  • 7 Latch
  • 8 PDU
  • 9 Tie-down element
  • 10 Cover element
  • 11 Receiving opening for ball element
  • 12 O-ring
  • 13 Fastening hole
  • 14 Reinforcing ribs
  • 20 Floor element
  • 21 Trough structure
  • 22 Outlet connection
  • 23 Cover surface
  • 24 Support web
  • 25 Tube sleeve
  • 26 Connection chamber
  • 27 Connecting cable
  • 30 Mounting region
  • 40 Functional rail
  • 41 Stop rail

Claims (16)

The invention claimed is:
1. A floor module for an aircraft cargo hold, the floor module comprising a cover element and a floor element which is spaced apart from the cover element at least in some segments and which is attached to an underside of the cover element, wherein the cover element is designed as an integrative surface element, wherein the cover element comprises receiving openings for receiving ball elements, wherein the cover element and the floor element are formed as a hybrid composite part, wherein the cover element and the floor element extend across the entire width of the cargo hold, wherein the floor element includes a first side connected to a rail and a second side having an upwardly curved section, which peripherally stiffen the floor module.
2. The floor module according to claim 1, wherein the floor element is connected to circumferential edges of the cover element and essentially tightly seals said floor element in the downward direction.
3. The floor module according to claim 1, wherein the floor element is designed for collecting and discharging liquids.
4. The floor module according to claim 1, wherein the cover element is formed from a first material and the floor element is formed from a second material, the first material forming the cover element having a thickness that is at least twice the thickness of the second material forming the floor element.
5. The floor module according to claim 1, wherein the cover element has, on at least one edge, an upwardly curved section for covering a portion of a fuselage of an aircraft.
6. The floor module according to claim 1, wherein connecting elements are provided between the cover element and the floor element.
7. The floor module according to claim 6, wherein the connecting elements comprise tube sleeves, by means of which fasteners are adapted to fasten tie-down elements directly to transverse beams of the cargo hold.
8. The floor module according to claim 1, wherein the cover element is fixedly connected to the floor element for common handling.
9. The floor module according to of claim 1, wherein the hybrid composite part of the cover element and/or the floor element comprises carbon fibres and/or glass fibres.
10. The floor module according to claim 1, wherein the rail which is attached to the floor element is provided with a freight-handling system.
11. The floor module according to claim 1, wherein the cover element comprises a peripherally mounted stop rail.
12. The floor module according to claim 1, wherein the floor element comprises connection chambers for connecting and/or extracting connection cables for freight-handling systems.
13. A use of a floor module according to claim 1 in the region of a cargo hold door.
14. The floor module according to claim 1, wherein the cover element is formed from a first material and the floor element is formed from a second material, the first material forming the cover element having a thickness that is at least three times the thickness of the second material forming the floor element.
15. The floor module according to claim 1, wherein the cover element is formed from a first material and the floor element is formed from a second material, the first material forming the cover element having a thickness that is at least five times the thickness of the second material forming the floor element.
16. The floor module according to claim 7, wherein the fasteners comprise screws.
US15/558,698 2015-03-20 2016-03-21 Floor module of an aircraft cargo hold Active 2036-08-17 US10773784B2 (en)

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
DE102015104230.4A DE102015104230B4 (en) 2015-03-20 2015-03-20 mounter
DE102015104230 2015-03-20
DE102015104230.4 2015-03-20
DE102015117571.1A DE102015117571B3 (en) 2015-10-15 2015-10-15 Floor module of an aircraft cargo hold
DE102015117571.1 2015-10-15
DE102015117571 2015-10-15
PCT/EP2016/056083 WO2016150891A1 (en) 2015-03-20 2016-03-21 Floor module of an aircraft cargo hold

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US20180111674A1 US20180111674A1 (en) 2018-04-26
US10773784B2 true US10773784B2 (en) 2020-09-15

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10940934B2 (en) * 2017-09-12 2021-03-09 Airbus Operations, GmbH Floor arrangement for a cabin of a vehicle
US11535359B2 (en) * 2019-01-29 2022-12-27 Goodrich Corporation Flexible and simple turnaround cargo handling assemblies
US11542005B2 (en) 2019-01-29 2023-01-03 Goodrich Corporation Quick-connect fittings for convertible cargo handling assemblies

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3481718A1 (en) * 2016-07-08 2019-05-15 Creative Solutions, Inc. Protective covers for use with aircraft cargo holds
DE102018108950B3 (en) * 2018-03-07 2019-03-21 Telair International Gmbh Cargo deck of an aircraft and method of making a floor module

Citations (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2173298A (en) 1938-04-30 1939-09-19 S H Thomson Mfg Company Roller construction
US3709450A (en) 1970-12-11 1973-01-09 Boeing Co Cargo loading system for aircraft
US3902583A (en) * 1970-09-21 1975-09-02 Jerry Laibson Load bearing tray
US4000870A (en) * 1975-09-08 1977-01-04 Western Gear Corporation Modular system for quick conversion of aircraft passenger compartments to cargo baggage/compartments
US4050655A (en) 1976-06-01 1977-09-27 The Boeing Company Cargo loading method and apparatus
US4696583A (en) * 1984-05-25 1987-09-29 The Boeing Company Ball support assembly
US5464086A (en) * 1994-03-03 1995-11-07 Transact International Inc. Ball transfer unit
DE19633032A1 (en) 1995-08-25 1997-02-27 Volkswagen Ag Fixing device to hold items on flat surfaces
EP0864489A2 (en) 1997-03-10 1998-09-16 Telair International GmbH Floor element
DE19720224A1 (en) 1997-03-24 1998-10-01 Telair Int Gmbh Ball mat for aircraft cargo decks
US5890582A (en) * 1996-06-25 1999-04-06 Fmc Corporation Ball deck
DE19812014C1 (en) 1998-03-19 1999-08-19 Daimler Chrysler Aerospace Tie system for freight in an aircraft cargo hold
US20030156914A1 (en) * 2002-02-13 2003-08-21 Telair International Gmbh Mounting apparatus for a transportation system
US20040218989A1 (en) * 2003-04-30 2004-11-04 Thomas Huber Cargo deck for an aircraft
EP1564141A1 (en) 2004-02-13 2005-08-17 Airbus France Aircraft seat rail and its production method
WO2005077755A1 (en) 2004-02-11 2005-08-25 Pfalz-Flugzeugwerke Gmbh Cargo-hold floor for aircraft
US20050224645A1 (en) * 2004-03-22 2005-10-13 Telair International Gmbh Cargo deck
GB2417619A (en) 2004-08-25 2006-03-01 Boeing Co Electrical bus for passenger seat electrical connectors
US20060065786A1 (en) * 2003-11-03 2006-03-30 Telair International Gmbh Conveyor apparatus for an aircraft cargo hold
DE102004044653A1 (en) 2004-09-15 2006-04-06 Airbus Deutschland Gmbh Carrier for freight on aircraft loading deck has base plate with integrated ball matt having fixings for freight and fastenings to transfer freight loads to aircraft structure
EP1646558A1 (en) 2003-07-18 2006-04-19 Telair International GmbH Floor for an aircraft cargo compartment an a method for the assembly thereof
US20060137294A1 (en) * 2004-01-13 2006-06-29 Waits Jr Bobby L Expanded fastener for a honeycomb structure and method of assembly
US20100230537A1 (en) * 2009-03-10 2010-09-16 Telair International Gmbh Floor Module of a Cargo Deck in the Hull of an Aircraft
DE102009012426A1 (en) 2009-03-10 2010-09-16 Telair International Gmbh roller conveyor
US20100230230A1 (en) * 2009-03-10 2010-09-16 Telair International Gmbh Roller Conveyor
US20110095572A1 (en) * 2009-10-28 2011-04-28 Eurocopter Honeycomb-structured floor panel for a vehicle, the panel incorporating a fastener element for fastening equipment of the vehicle
US20120061511A1 (en) * 2010-08-13 2012-03-15 Telair International Gmbh Cargo hold floor and aircraft having a cargo hold floor
US20120304579A1 (en) * 2011-06-06 2012-12-06 Steven Dezoete Removable Mid-Section Production Floorboard
US20120312926A1 (en) * 2011-06-10 2012-12-13 Telair International Gmbh Cargo Deck, Cargo Loading System and Method for Loading/Unloading a Cargo Hold
DE102012005353A1 (en) 2012-03-16 2013-09-19 Airbus Operations Gmbh Aircraft fuselage structure with transverse profiles and truss structure
DE102012008853A1 (en) 2012-04-28 2013-10-31 Daimler Ag Floor module for use in hybrid construction for structure of motor vehicle, comprises floor element and plastic element formed adjacent to each other in predominant surface area of floor module and spaced apart by reinforcing element
US20130297065A1 (en) * 2011-01-19 2013-11-07 Telair International Gmbh Loading System for an Aircraft and Method for Conveying a Piece of Cargo on a Cargo Deck
US20130313073A1 (en) * 2011-02-18 2013-11-28 Telair International Gmbh Freight Loading System and Method for Controlling a Plurality of Freight Handling Devices
US20130340364A1 (en) * 2012-06-26 2013-12-26 Airbus Operations Gmbh Floor panel with integrated cable channel
US20130340601A1 (en) * 2006-01-31 2013-12-26 William A. Townsend Structural panel with ballistic protection
US8851488B2 (en) * 2012-06-15 2014-10-07 Iscar Gse Corp. Modular cargo dolly
DE102013207645A1 (en) 2013-04-26 2014-10-30 Airbus Operations Gmbh Cargo floor module and means of transport
CA2859329A1 (en) 2013-09-03 2015-03-03 The Boeing Company Structural inserts for honeycomb structures
US9238551B2 (en) * 2013-04-02 2016-01-19 Kalitta Air Llc Ball transfer unit for cargo bay
US20160244186A1 (en) * 2014-06-30 2016-08-25 The Boeing Company Flight test equipment installation system and method
US9963232B2 (en) * 2015-01-26 2018-05-08 Mitsubishi Aircraft Corporation Aircraft floor panel with ball transfer unit
US10059523B1 (en) * 2017-02-09 2018-08-28 Goodrich Corporation Modular standard configuration ballpanel

Patent Citations (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2173298A (en) 1938-04-30 1939-09-19 S H Thomson Mfg Company Roller construction
US3902583A (en) * 1970-09-21 1975-09-02 Jerry Laibson Load bearing tray
US3709450A (en) 1970-12-11 1973-01-09 Boeing Co Cargo loading system for aircraft
US4000870A (en) * 1975-09-08 1977-01-04 Western Gear Corporation Modular system for quick conversion of aircraft passenger compartments to cargo baggage/compartments
US4050655A (en) 1976-06-01 1977-09-27 The Boeing Company Cargo loading method and apparatus
US4696583A (en) * 1984-05-25 1987-09-29 The Boeing Company Ball support assembly
US5464086A (en) * 1994-03-03 1995-11-07 Transact International Inc. Ball transfer unit
DE19633032A1 (en) 1995-08-25 1997-02-27 Volkswagen Ag Fixing device to hold items on flat surfaces
US5890582A (en) * 1996-06-25 1999-04-06 Fmc Corporation Ball deck
EP0864489A2 (en) 1997-03-10 1998-09-16 Telair International GmbH Floor element
DE19720224A1 (en) 1997-03-24 1998-10-01 Telair Int Gmbh Ball mat for aircraft cargo decks
EP0912394A1 (en) 1997-03-24 1999-05-06 Telair International GmbH Ball mat
US6125984A (en) * 1997-03-24 2000-10-03 Telair International Gmbh Ball mat
DE19812014C1 (en) 1998-03-19 1999-08-19 Daimler Chrysler Aerospace Tie system for freight in an aircraft cargo hold
US20030156914A1 (en) * 2002-02-13 2003-08-21 Telair International Gmbh Mounting apparatus for a transportation system
US6926481B2 (en) 2002-02-13 2005-08-09 Telair International Gmbh Mounting apparatus for a transportation system
US20040218989A1 (en) * 2003-04-30 2004-11-04 Thomas Huber Cargo deck for an aircraft
US20060231681A1 (en) * 2003-07-18 2006-10-19 Thomas Huber Floor for an aircraft cargo compartment and method for the assembly thereof
US8226034B2 (en) 2003-07-18 2012-07-24 Telair International Gmbh Cargo deck and a method for assembling said deck
EP1646556A1 (en) 2003-07-18 2006-04-19 Telair International GmbH Cargo deck for receiving a load in the cargo hold of an aircraft
EP1646558A1 (en) 2003-07-18 2006-04-19 Telair International GmbH Floor for an aircraft cargo compartment an a method for the assembly thereof
US20060065786A1 (en) * 2003-11-03 2006-03-30 Telair International Gmbh Conveyor apparatus for an aircraft cargo hold
US20060137294A1 (en) * 2004-01-13 2006-06-29 Waits Jr Bobby L Expanded fastener for a honeycomb structure and method of assembly
DE102004006648A1 (en) 2004-02-11 2005-09-08 Pfalz-Flugzeugwerke Gmbh Cargo hold floor for aircraft
WO2005077755A1 (en) 2004-02-11 2005-08-25 Pfalz-Flugzeugwerke Gmbh Cargo-hold floor for aircraft
EP1564141A1 (en) 2004-02-13 2005-08-17 Airbus France Aircraft seat rail and its production method
DE602005001782T2 (en) 2004-02-13 2008-04-30 Airbus France Aircraft seat rail and its manufacturing process
US20050224645A1 (en) * 2004-03-22 2005-10-13 Telair International Gmbh Cargo deck
GB2417619A (en) 2004-08-25 2006-03-01 Boeing Co Electrical bus for passenger seat electrical connectors
DE102004044653A1 (en) 2004-09-15 2006-04-06 Airbus Deutschland Gmbh Carrier for freight on aircraft loading deck has base plate with integrated ball matt having fixings for freight and fastenings to transfer freight loads to aircraft structure
US20130340601A1 (en) * 2006-01-31 2013-12-26 William A. Townsend Structural panel with ballistic protection
US20100230230A1 (en) * 2009-03-10 2010-09-16 Telair International Gmbh Roller Conveyor
DE102009012426A1 (en) 2009-03-10 2010-09-16 Telair International Gmbh roller conveyor
US20100230537A1 (en) * 2009-03-10 2010-09-16 Telair International Gmbh Floor Module of a Cargo Deck in the Hull of an Aircraft
US20110095572A1 (en) * 2009-10-28 2011-04-28 Eurocopter Honeycomb-structured floor panel for a vehicle, the panel incorporating a fastener element for fastening equipment of the vehicle
US20120061511A1 (en) * 2010-08-13 2012-03-15 Telair International Gmbh Cargo hold floor and aircraft having a cargo hold floor
US20130297065A1 (en) * 2011-01-19 2013-11-07 Telair International Gmbh Loading System for an Aircraft and Method for Conveying a Piece of Cargo on a Cargo Deck
US20130313073A1 (en) * 2011-02-18 2013-11-28 Telair International Gmbh Freight Loading System and Method for Controlling a Plurality of Freight Handling Devices
US20120304579A1 (en) * 2011-06-06 2012-12-06 Steven Dezoete Removable Mid-Section Production Floorboard
US20120312926A1 (en) * 2011-06-10 2012-12-13 Telair International Gmbh Cargo Deck, Cargo Loading System and Method for Loading/Unloading a Cargo Hold
DE102012005353A1 (en) 2012-03-16 2013-09-19 Airbus Operations Gmbh Aircraft fuselage structure with transverse profiles and truss structure
WO2013135855A1 (en) 2012-03-16 2013-09-19 Airbus Operations Gmbh Aircraft fuselage structure comprising transverse profiles and framework structure
DE102012008853A1 (en) 2012-04-28 2013-10-31 Daimler Ag Floor module for use in hybrid construction for structure of motor vehicle, comprises floor element and plastic element formed adjacent to each other in predominant surface area of floor module and spaced apart by reinforcing element
US8851488B2 (en) * 2012-06-15 2014-10-07 Iscar Gse Corp. Modular cargo dolly
US20130340364A1 (en) * 2012-06-26 2013-12-26 Airbus Operations Gmbh Floor panel with integrated cable channel
EP2679485A1 (en) 2012-06-26 2014-01-01 Airbus Operations GmbH Floor panel with integrated cable channel
US9238551B2 (en) * 2013-04-02 2016-01-19 Kalitta Air Llc Ball transfer unit for cargo bay
DE102013207645A1 (en) 2013-04-26 2014-10-30 Airbus Operations Gmbh Cargo floor module and means of transport
CA2859329A1 (en) 2013-09-03 2015-03-03 The Boeing Company Structural inserts for honeycomb structures
US20160244186A1 (en) * 2014-06-30 2016-08-25 The Boeing Company Flight test equipment installation system and method
US9963232B2 (en) * 2015-01-26 2018-05-08 Mitsubishi Aircraft Corporation Aircraft floor panel with ball transfer unit
US10059523B1 (en) * 2017-02-09 2018-08-28 Goodrich Corporation Modular standard configuration ballpanel

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
English Translation of International Preliminary Report on Patentability, PCT/EP2016/056083, dated Sep. 26, 2017.
Search Report and Written Opinion issued in App. No. PCT/EP2016/056083 (dated 2016).

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10940934B2 (en) * 2017-09-12 2021-03-09 Airbus Operations, GmbH Floor arrangement for a cabin of a vehicle
US11535359B2 (en) * 2019-01-29 2022-12-27 Goodrich Corporation Flexible and simple turnaround cargo handling assemblies
US11542005B2 (en) 2019-01-29 2023-01-03 Goodrich Corporation Quick-connect fittings for convertible cargo handling assemblies

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